Cold Air Performance Of Compressor Drive Turbine Of Department Of Energy Upgraded Automobile Gas Turbine Engine 1

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Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1: Volute-manifold and Stator Performance

Author : Anonim
Publisher : Unknown
Page : 24 pages
File Size : 44,5 Mb
Release : 1981
Category : Electronic
ISBN : NASA:31769000551823

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Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1: Volute-manifold and Stator Performance by Anonim Pdf

The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. (Author).

Energy Research Abstracts

Author : Anonim
Publisher : Unknown
Page : 1430 pages
File Size : 50,8 Mb
Release : 1984
Category : Power resources
ISBN : CUB:U183019899814

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Energy Research Abstracts by Anonim Pdf

Semiannual, with semiannual and annual indexes. References to all scientific and technical literature coming from DOE, its laboratories, energy centers, and contractors. Includes all works deriving from DOE, other related government-sponsored information, and foreign nonnuclear information. Arranged under 39 categories, e.g., Biomedical sciences, basic studies; Biomedical sciences, applied studies; Health and safety; and Fusion energy. Entry gives bibliographical information and abstract. Corporate, author, subject, report number indexes.

NASA Technical Memorandum

Author : Anonim
Publisher : Unknown
Page : 28 pages
File Size : 48,7 Mb
Release : 1982
Category : Aeronautics
ISBN : MINN:319510008452917

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NASA Technical Memorandum by Anonim Pdf

Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. II. Stage Performance

Author : Anonim
Publisher : Unknown
Page : 28 pages
File Size : 51,9 Mb
Release : 1982
Category : Electronic
ISBN : UIUC:30112008540574

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Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. II. Stage Performance by Anonim Pdf

The aerodynamic performance of the compressor-drive turbine of the DOE Upgraded Gas Turbine (UGT) engine was determined in low-temperature air. The nominal turbine-inlet temperature was 320 K. Inlet pressures were varied between 0.4 and 2.4 bars absolute. The turbine blading used in these tests consisted of duplicates of the stator and rotor castings used in development engine tests. The as-received cast rotor blades had a significantly thicker profile than design and a fairly rough surface finish. Because of these blade profile imperfections three turbine rotor configurations were evaluated. These were the as-cast rotor, a reduced-roughness rotor, and a rotor with the blade profiles thinned to near the design profile. Tests to determine the effect of Reynolds number on the turbine performance were also made. (Author).

Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1

Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 24 pages
File Size : 42,7 Mb
Release : 2018-07-20
Category : Electronic
ISBN : 1723398764

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Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1 by National Aeronautics and Space Administration (NASA) Pdf

The aerodynamic performance of the inlet manifold and stator assembly of the compressor drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. Roelke, R. J. and Haas, J. E. Glenn Research Center NASA-TM-82682, DOE/NASA/1011-34, E-572, AVRADCOM-TR-80-C-20 EC-77-A-31-1011; RTOP 505-32-2B

Energy

Author : Anonim
Publisher : Unknown
Page : 322 pages
File Size : 48,9 Mb
Release : 1983
Category : Fuel
ISBN : STANFORD:36105024717204

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Energy by Anonim Pdf

Technical Abstract Bulletin

Author : Anonim
Publisher : Unknown
Page : 224 pages
File Size : 48,6 Mb
Release : 1981
Category : Science
ISBN : CORNELL:31924057177549

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Technical Abstract Bulletin by Anonim Pdf

Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 2

Author : National Aeronautics and Space Administration (NASA)
Publisher : Createspace Independent Publishing Platform
Page : 24 pages
File Size : 47,8 Mb
Release : 2018-07-20
Category : Electronic
ISBN : 1723419044

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Cold-Air Performance of Compressor-Drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 2 by National Aeronautics and Space Administration (NASA) Pdf

The aerodynamic performance of the compressor-drive turbine of the DOE upgraded gas turbine engine was determined in low temperature air. The as-received cast rotor blading had a significantly thicker profile than design and a fairly rough surface finish. Because of these blading imperfections a series of stage tests with modified rotors were made. These included the as-cast rotor, a reduced-roughness rotor, and a rotor with blades thinned to near design. Significant performance changes were measured. Tests were also made to determine the effect of Reynolds number on the turbine performance. Comparisons are made between this turbine and the compressor-drive turbine of the DOE baseline gas turbine engine. Roelke, R. J. and Haas, J. E. Glenn Research Center NASA-TM-82818, DOE/NASA/1011-36, NAS 1.15:82818, AVRADCOM-TR-82-C-1 EC-77-A-31-1011